A review of numerical simulation and modeling of combustion in scramjets

Clark, Ryan J.; Shrestha, SO Bade

doi:10.1177/0954410014541249

Cited by 9 publications

(4 citation statements)

References 39 publications

(96 reference statements)

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“…In recent decades, the scramjet engine receives attention as the potential candidate for future hypersonic propulsion vehicles(Ben-Yakar and Hanson, 2001; Clark and Bade Shrestha, 2015; Viaud and Mestre, 1966). In the scramjet engine, the fuel injection system plays a pivotal role in enhancing the fuel-air mixing attributes and improves the overall combustion performance as well.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

Jeyakumar

Jayaraman

Sivakumar

et al. 2021

AEAT

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Purpose This paper aims to study the influences of hydrogen jet pressure on flow features of a strut-based injector in a scramjet combustor under-reacting cases are numerically investigated in this study. Design/methodology/approach The numerical analysis is carried out using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport k-ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters such as the shock wave pattern, wall pressures and static temperature across the combustor are validated with the reported experiments. The results comply with the range, indicating the adopted simulation method can be extended for other investigations as well. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency and total pressure loss. Findings The results revealed that the augmentation of hydrogen jet pressure via variation in flame features increases the static pressure in the vicinity of the strut and destabilize the normal shock wave position. Indeed, the pressure of the mainstream flow drives the shock wave toward the upstream direction. The study perceived that once the hydrogen jet pressure is reached 4 bar, the incoming flow attains a subsonic state due to the movement of normal shock wave ahead of the strut. It is noticed that the increase in hydrogen jet pressure in the supersonic flow field improves the jet penetration rate in the lateral direction of the flow and also increases the total pressure loss as compared with the baseline injection pressure condition. Practical implications The outcome of this research provides the influence of fuel injection pressure variations in the supersonic combustion phenomenon of hypersonic vehicles. Originality/value This paper substantiates the effect of increasing hydrogen jet pressure in the reacting supersonic airstream on the performance of a scramjet combustor.

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Section: Introductionmentioning

confidence: 99%

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

Jeyakumar

Jayaraman

Sivakumar

et al. 2021

AEAT

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“…In recent years, there has been considerable attention to the scramjet engine, which is a potential candidate for future hypersonic propulsion vehicles [1][2][3]. The fuel injection system plays a pivotal role in enhancing the fuel-air mixing attributes and improving the overall combustion performance of the scramjet engine.…”

Section: Introductionmentioning

confidence: 99%

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

et al. 2021

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This paper focuses on the influence of ramp locations upstream of a strut-based scramjet combustor under reacting flow conditions that are numerically investigated. In contrast, a computational study is adopted using Reynolds Averaged Navier Stokes (RANS) equations with the Shear Stress Transport (SST) k-ω turbulence model. The numerical results of the Deutsches Zentrum für Luft- und Raumfahrt or German Aerospace Centre (DLR) scramjet model are validated with the reported experimental values that show compliance within the range, indicating that the adopted simulation method can be extended for other investigations as well. The performance of the ramps in the strut-based scramjet combustor is analyzed based on parameters such as wall pressures, combustion efficiency and total pressure loss at various axial locations of the combustor. From the numerical shadowgraph, more shock interactions are observed upstream of the strut injection region for the ramp cases, which decelerates the flow downstream, and additional shock reflections with less intensity are also noticed when compared with the DLR scramjet model. The shock reflection due to the ramps enhances the hydrogen distribution in the spatial direction. The ignition delay is noticed for ramp combustors due to the deceleration of flow compared to the baseline strut only scramjet combustor. However, a higher flame temperature is observed with the ramp combustor. Because more shock interactions arise from the ramps, a marginal increase in the total pressure loss is observed for ramp combustors when compared to the baseline model.

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“…In recent decades, the scramjet engine received attention as the potential candidate for future hypersonic propulsion vehicles. 1,2,3 In the scramjet engine, the fuel injection system plays an important part in improving the mixing of working fluid and also improves the overall combustion performance. 4,5 A robust flame holding mechanism is needed owing to the short residence time of airflow in the scramjet combustor.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

2021

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This study aims at investigating the effect of a multistrut-based hydrogen injector in a scramjet combustor underreacting case. The numerical analysis is carried out using two-dimensional Reynolds-averaged Navier-Stokes equations with the Shear Stress Transport k − ω turbulence model in contention to comprehend the flow physics during scramjet combustion. The three major parameters, such as the shock wave pattern, wall pressures, and static temperature across the combustor, are validated with the reported experimental results. The results comply with the range, indicating that the adopted simulation method for single strut injection can be extended for other investigations. It is noticed that with multistrut injectors, as hydrogen jet pressure increases in the supersonic flow field, the jet penetration rate in the lateral direction of the flow and the total pressure loss as compared with the baseline injection pressure conditions has increased. The supersonic flow characteristics are determined based on the flow properties, combustion efficiency, mixing efficiency, and total pressure loss. Compared with the single-strut output of a scramjet combustor, multistruts inclusion increased the combustion efficiency by almost 18%, the mixing efficiency attained the maximum with 16% fewer lengths. The total pressure loss in single-strut is 14% lower than that of multistrut.

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A review of numerical simulation and modeling of combustion in scramjets

Cited by 9 publications

References 39 publications

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

Numerical investigations on the hydrogen jet pressure variations in a strut based scramjet combustor

The Combustion Characteristics of Double Ramps in a Strut-Based Scramjet Combustor

Numerical investigations on the performance of a multistrut hydrogen injector in a scramjet combustor

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